Joukovsky f=0% t=9% (joukowsk0009-jf) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Joukovsky f=0% t=9% (joukowsk0009-jf) Reynolds number: 200,000 Max Cl/Cd: 44.23 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-joukowsk0009-jf-200000.txt Download as CSV file: xf-joukowsk0009-jf-200000.csv |
XFOIL Version 6.96
Calculated polar for: Joukovsky f=0% t=9%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.8969 0.06462 0.06071 -0.0104 1.0000 0.0346
-10.500 -0.9182 0.05940 0.05537 -0.0125 1.0000 0.0343
-10.250 -0.9370 0.05491 0.05068 -0.0127 1.0000 0.0340
-10.000 -0.9486 0.05011 0.04556 -0.0128 1.0000 0.0339
-9.750 -0.9527 0.04562 0.04067 -0.0126 1.0000 0.0340
-9.500 -0.9483 0.04241 0.03696 -0.0120 1.0000 0.0347
-9.250 -0.9432 0.03787 0.03193 -0.0114 1.0000 0.0354
-9.000 -0.9308 0.03382 0.02756 -0.0110 1.0000 0.0362
-8.750 -0.9126 0.03127 0.02479 -0.0105 1.0000 0.0372
-8.500 -0.8922 0.02923 0.02253 -0.0100 1.0000 0.0385
-8.250 -0.8706 0.02734 0.02040 -0.0095 1.0000 0.0401
-8.000 -0.8477 0.02586 0.01866 -0.0090 1.0000 0.0424
-7.750 -0.8247 0.02405 0.01655 -0.0084 1.0000 0.0447
-7.500 -0.8016 0.02220 0.01469 -0.0080 1.0000 0.0474
-7.250 -0.7770 0.02109 0.01348 -0.0076 1.0000 0.0507
-7.000 -0.7513 0.02034 0.01253 -0.0071 1.0000 0.0544
-6.750 -0.7283 0.01861 0.01088 -0.0066 1.0000 0.0592
-6.500 -0.7028 0.01778 0.00995 -0.0062 1.0000 0.0647
-6.250 -0.6787 0.01664 0.00885 -0.0058 1.0000 0.0720
-6.000 -0.6536 0.01573 0.00792 -0.0053 1.0000 0.0808
-5.750 -0.6284 0.01494 0.00714 -0.0050 1.0000 0.0932
-5.500 -0.6035 0.01407 0.00640 -0.0047 1.0000 0.1102
-5.250 -0.5781 0.01332 0.00574 -0.0044 1.0000 0.1352
-5.000 -0.5528 0.01256 0.00518 -0.0042 1.0000 0.1695
-4.750 -0.5272 0.01192 0.00474 -0.0040 1.0000 0.2122
-4.500 -0.5013 0.01137 0.00439 -0.0039 1.0000 0.2581
-4.250 -0.4753 0.01091 0.00410 -0.0037 1.0000 0.3036
-4.000 -0.4491 0.01052 0.00387 -0.0034 1.0000 0.3472
-3.750 -0.4229 0.01018 0.00367 -0.0031 1.0000 0.3885
-3.500 -0.3966 0.00989 0.00350 -0.0028 1.0000 0.4286
-3.250 -0.3705 0.00962 0.00337 -0.0024 1.0000 0.4659
-3.000 -0.3444 0.00939 0.00325 -0.0020 1.0000 0.5021
-2.750 -0.3187 0.00917 0.00316 -0.0015 1.0000 0.5362
-2.500 -0.2933 0.00897 0.00309 -0.0009 1.0000 0.5690
-2.250 -0.2685 0.00879 0.00304 -0.0002 1.0000 0.6006
-2.000 -0.2447 0.00864 0.00301 0.0007 1.0000 0.6313
-1.750 -0.2223 0.00851 0.00301 0.0018 1.0000 0.6609
-1.500 -0.2016 0.00841 0.00305 0.0031 1.0000 0.6900
-1.250 -0.1621 0.00836 0.00312 0.0007 0.9871 0.7225
-1.000 -0.1173 0.00831 0.00319 -0.0024 0.9696 0.7543
-0.750 -0.0782 0.00826 0.00324 -0.0041 0.9469 0.7836
-0.500 -0.0459 0.00823 0.00328 -0.0041 0.9211 0.8113
-0.250 -0.0211 0.00822 0.00331 -0.0025 0.8933 0.8386
0.000 0.0000 0.00822 0.00331 0.0000 0.8658 0.8659
0.250 0.0211 0.00822 0.00331 0.0025 0.8386 0.8933
0.500 0.0459 0.00823 0.00328 0.0041 0.8114 0.9211
0.750 0.0782 0.00826 0.00324 0.0041 0.7836 0.9469
1.000 0.1173 0.00831 0.00319 0.0023 0.7543 0.9696
1.250 0.1621 0.00836 0.00312 -0.0007 0.7225 0.9871
1.500 0.2017 0.00841 0.00305 -0.0031 0.6900 1.0000
1.750 0.2224 0.00851 0.00301 -0.0018 0.6609 1.0000
2.000 0.2448 0.00864 0.00301 -0.0007 0.6312 1.0000
2.250 0.2686 0.00879 0.00304 0.0001 0.6007 1.0000
2.500 0.2934 0.00897 0.00309 0.0008 0.5690 1.0000
2.750 0.3188 0.00917 0.00316 0.0014 0.5361 1.0000
3.000 0.3445 0.00939 0.00325 0.0019 0.5021 1.0000
3.250 0.3706 0.00962 0.00337 0.0024 0.4659 1.0000
3.500 0.3967 0.00989 0.00350 0.0028 0.4286 1.0000
3.750 0.4229 0.01018 0.00367 0.0031 0.3885 1.0000
4.000 0.4492 0.01052 0.00387 0.0034 0.3472 1.0000
4.250 0.4753 0.01091 0.00410 0.0036 0.3037 1.0000
4.500 0.5014 0.01137 0.00439 0.0039 0.2582 1.0000
4.750 0.5272 0.01192 0.00474 0.0040 0.2121 1.0000
5.000 0.5528 0.01256 0.00518 0.0042 0.1695 1.0000
5.250 0.5781 0.01332 0.00574 0.0044 0.1352 1.0000
5.500 0.6035 0.01407 0.00640 0.0047 0.1102 1.0000
5.750 0.6284 0.01494 0.00715 0.0050 0.0932 1.0000
6.000 0.6537 0.01573 0.00792 0.0053 0.0809 1.0000
6.250 0.6787 0.01663 0.00885 0.0058 0.0719 1.0000
6.500 0.7027 0.01777 0.00995 0.0062 0.0647 1.0000
6.750 0.7281 0.01861 0.01088 0.0067 0.0592 1.0000
7.000 0.7511 0.02034 0.01253 0.0072 0.0544 1.0000
7.250 0.7767 0.02109 0.01348 0.0076 0.0507 1.0000
7.500 0.8013 0.02220 0.01469 0.0081 0.0475 1.0000
7.750 0.8243 0.02405 0.01655 0.0085 0.0447 1.0000
8.000 0.8471 0.02584 0.01863 0.0091 0.0424 1.0000
8.250 0.8699 0.02731 0.02037 0.0096 0.0401 1.0000
8.500 0.8914 0.02920 0.02249 0.0102 0.0385 1.0000
8.750 0.9116 0.03125 0.02478 0.0107 0.0372 1.0000
9.000 0.9297 0.03376 0.02750 0.0112 0.0362 1.0000
9.250 0.9424 0.03772 0.03177 0.0117 0.0354 1.0000
9.500 0.9471 0.04247 0.03701 0.0122 0.0348 1.0000
9.750 0.9516 0.04565 0.04067 0.0128 0.0342 1.0000
10.000 0.9481 0.04992 0.04536 0.0131 0.0339 1.0000
10.250 0.9365 0.05476 0.05052 0.0130 0.0341 1.0000
10.500 0.9180 0.05928 0.05524 0.0128 0.0343 1.0000
10.750 0.8976 0.06437 0.06045 0.0108 0.0346 1.0000
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Polar data table (+)
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